Meredith Effect Boundary Layer Energisation System

Abstract

An aircraft including an aft-mounted boundary layer energisation system is shown. The system comprises a nacelle arranged around a tailcone of the aircraft which thereby defines a duct, the duct having, in axial flow series, an intake, a heat exchanger, and a nozzle, and no turbomachinery therein, whereby the system energises a boundary layer of the aircraft by means of Meredith effect.

1 . An aircraft including an aft-mounted boundary layer energisation system, comprising a nacelle arranged around a tailcone of the aircraft which thereby defines a duct, the duct having, in axial flow series, an intake, a heat exchanger, and a nozzle, and no turbomachinery therein, whereby the system energises a boundary layer of the aircraft by means of Meredith effect. 
     
     
         2 . The aircraft of  claim 1 , in which the heat exchanger forms part of a cooling loop of an environmental control system of the aircraft. 
     
     
         3 . The aircraft of  claim 1 , in which the heat exchanger forms part of a cooling loop for an electrical generator located in the fuselage of the aircraft. 
     
     
         4 . The aircraft of  claim 1 , in which the electrical generator is driven by a gas turbine engine. 
     
     
         5 . The aircraft of  claim 1 , in which the gas turbine engine also forms part of the cooling loop. 
     
     
         6 . The aircraft of  claim 1 , in which the heat exchanger extends fully across the duct from the fuselage to the nacelle. 
     
     
         7 . The aircraft of  claim 1 , in which the heat exchanger connects the nacelle to the fuselage. 
     
     
         8 . The aircraft of  claim 1 , in which the nozzle is a convergent nozzle.